US20090173831A1 - Method for manufacturing a solar module in orbit - Google Patents
Method for manufacturing a solar module in orbit Download PDFInfo
- Publication number
- US20090173831A1 US20090173831A1 US11/409,697 US40969706A US2009173831A1 US 20090173831 A1 US20090173831 A1 US 20090173831A1 US 40969706 A US40969706 A US 40969706A US 2009173831 A1 US2009173831 A1 US 2009173831A1
- Authority
- US
- United States
- Prior art keywords
- space
- orbit
- solar
- earth
- empty
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 34
- 238000000034 method Methods 0.000 title claims description 15
- 230000005484 gravity Effects 0.000 claims abstract description 20
- 235000015842 Hesperis Nutrition 0.000 claims description 6
- 235000012633 Iberis amara Nutrition 0.000 claims description 6
- 238000003491 array Methods 0.000 abstract description 15
- 239000002828 fuel tank Substances 0.000 abstract description 3
- 241000196324 Embryophyta Species 0.000 description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- 239000001257 hydrogen Substances 0.000 description 4
- 229910052739 hydrogen Inorganic materials 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004566 building material Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 210000000078 claw Anatomy 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/12—Artificial satellites; Systems of such satellites; Interplanetary vehicles manned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/14—Space shuttles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/405—Ion or plasma engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49002—Electrical device making
- Y10T29/49016—Antenna or wave energy "plumbing" making
Definitions
- the present invention relates generally to the creation of a geosynchronous Solar Power Satellite System, and more particularly to the creation of an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels, modular transmitter arrays and truss structures.
- a method of creating a geosynchronous solar power satellite system from a low earth orbit structure with artificial gravity and closed ecology that links re-manufactured expended rocket boosters with solar cells created on earth into modular solar panels. It also links re-manufactured expended rocket boosters with microwave transmitter elements created on earth into modular transmitter arrays. Both the solar panels and transmitter arrays are transported to geosynchronous orbit by electric engines (like ion engines).
- the low earth orbit manufacturing facility is created. Empty external tanks from Space Shuttle launches are collected in low earth orbit. They are then joined together, filled with habitat, manufacturing, environment recycling modules and engines. They are then rotated to create an artificial “mars normal” gravity environment.
- the facility is used to manufacture the modular components of the Solar Power Satellite System. Additional empty external tanks and expended rocket boosters are collected. They are re-manufactured and mated to solar cells manufactured on earth and launched to low earth orbit. Modular solar panels are created. Truss structures are created. Modular transmitter arrays are created by mating transmitter arrays manufactured on earth and launched to low earth orbit, to truss structures. These modular solar panels and modular transmitter arrays are moved to geosynchronous orbit by unmanned vehicles using electric powered engines (like ion engines). Then the solar power panels and transmitter arrays are linked together in geosynchronous orbit to beam power back to earth.
- FIG. 1 discloses a prior art solar power satellite system
- FIG. 2 shows an External Tank (ET) from a Space Shuttle launch. It has been outfitted with 2 solar power, electric engine (like ion drive) devices for station keeping;
- E External Tank
- FIG. 3 shows the low earth orbit (LEO) artificial gravity, closed ecology, multi-use structure for manufacturing the solar power panels, the truss structures, and the transmitter arrays;
- LEO low earth orbit
- FIG. 4 shows a cutaway diagram of an “outer ET” in the previous diagram where, upon rotation, there will be simulated a “mars-normal” artificial gravity environment
- FIG. 5 shows the low earth orbit (LEO) artificial gravity, closed ecology, multi-use structure with a modular solar power panel constructed and ready to be taken to geosynchronous orbit (GEO);
- LEO low earth orbit
- GEO geosynchronous orbit
- FIG. 6 shows the RANGER NPV space vehicle of the prior art from the Space Systems Laboratory with its hands grasping an object
- FIG. 7 shows the design for a truss structure of the prior art
- FIG. 8 shows a sub-panel of solar cells being rolled up for construction of the modular solar power panel
- FIG. 9 shows a collection of modular solar power panels with truss structures, connected to a Ranger for transport to geosynchronous orbit (GEO);
- GEO geosynchronous orbit
- FIG. 10 shows a Solar Power Satellite, with collection array, and transmitter
- FIG. 11 shows a cutaway of the Space Shuttle External Tank(ET) of the prior art
- FIG. 12 shows a Space Shuttle of the prior art
- FIG. 13 is a picture label index.
- an empty external tank (ET) # 1 ( FIG. 2 ) from the Space Shuttle is not discarded upon the Shuttle's launch to the International Space Station (ISS). Instead, the empty external tank (ET) is taken into orbit with the Space Shuttle. About 30 miles short of the International Space Station (ISS), the Shuttle disconnects and undocks from the external tank (ET).
- the external tank (ET) is fitted by the Shuttle Manipulator Arm # 37 (a standard part of the Space Shuttle) with a station keeping device, which consists of a girdle of solar power cells # 18 ( FIG. 2 ) that connects to an ion engine # 2 ( FIG. 2 ).
- the Shuttle crew opens the cargo bay doors # 38 ( FIG. 12 ), and take out a wraparound solar panel with an ion engine # 18 , 2 ( FIG. 2 ), using the Shuttle Manipulator Arm # 37 ( FIG. 12 ). With the Shuttle Manipulator Arm # 37 ( FIG. 12 ), the Shuttle astronauts attach the wraparound solar panel with ion engine # 18 , 2 to the external tank (ET).
- the Space Shuttle still attached to its external tank (ET) rendezvous with the 3 stored ETs and the commercial launch payload at the site short of the ISS.
- the Shuttle uncouples from its attached ET.
- the ET is positioned perpendicularly to another ET.
- the base end of one ET # 36 ( FIG. 11 ) is attached to the middle of another ET, creating a “T” like structure. This task is repeated with the other pair of ETs so that 2 “T” structures have been created.
- the habitat # 10 ( FIG. 4 ), manufacturing # 12 , 13 ( FIG. 4 ) and ecology # 11 ( FIG. 4 ) modules are loaded into the empty hydrogen tank # 34 ( FIG. 11 ) of those ETs and then the base ends # 36 are reattached.
- the nose ends # 35 ( FIG. 11 ) of the ET that forms the base of the “T” are attached to the docking port # 3 ( FIG. 3 ) module.
- the structural cables # 4 ( FIG. 3 ) are attached.
- the manipulator robots # 5 - 7 ( FIG. 3 ) are attached to the structural cables # 4 .
- the solar power assembly tracks # 16 ( FIG. 3 ) are attached and then the solar panel assembly robots # 17 ( FIG. 3 ) are attached to the solar power assembly tracks # 16 .
- the ion engines # 2 ( FIG. 3 ) are repositioned and then they are fired up to start the rotation process to generate artificial gravity.
- the manufacturing facility makes if possible to cheaply and easily remanufacture the empty fuel tanks and booster rockets into solar panels because of its artificial gravity and closed ecology.
- Many closed ecologies have already been tested here on earth, but only in our gravity environment.
- Our manufacturing expertise is only in our gravity environment.
- An artificial gravity environment similar to that of Mars could be generated by a structure rotating twice a minute that has a diameter of 300 feet (approx. 100 meters). This is the artificial gravity environment that's best for the manufacturing structure.
- the martian 0.4 g environment will not have a significant impact on the technologies developed on earth, either the closed-ecology or manufacturing technologies required to build the Solar Power Satellite project.
- the working/living environment will be inside the hydrogen tank # 34 ( FIG. 11 ), in the ET, and so doubly shielded from space.
- the hydrogen tank # 34 is 100 feet long by 27 feet in diameter. Turned into 2 floors, it would be about 5000 square feet per tank. Inside, various parts would be setup for habitat # 10 ( FIG. 4 ), foundry # 13 ( FIG. 4 ), machine shop # 12 ( FIG. 4 ) and closed-ecology equipment and facilities # 11 ( FIG. 4 ).
- Solar power modules 100 meters square, are an output product of the manufacturing facility.
- the solar cells are manufactured on earth. They will be launched into LEO, aimed at the manufacturing facility. In this preferred embodiment, they will be captured and loaded into the facility.
- a space tug ( FIG. 6 ) will capture the cargo and transfer it to the manipulator robots # 5 - 7 ( FIG. 3 ).
- the rocket that delivers the solar cells will be cut up and taken into the facility. Machines have been designed to cut ET's into cylindrical chunks. These chunks will be grasped by the manipulator robots # 5 - 7 ( FIG. 3 ). These manipulator robots # 5 - 7 ( FIG. 3 ) will be teleoperable and be attached to and move up and down the structural cables # 4 ( FIG.
- the materials in the stream are already quite refined, being composed of empty fuel tanks, expended rocket boosters and captured “space junk”.
- Most of the stream is made of aluminum, which is light and easily re-melted and reformed at low (700 deg F.) temperatures.
- the material stream will be melted down in the foundry # 13 ( FIG. 4 ), and turned into building material.
- the building pieces consist of metal sheets, pipes and pipe holders.
- the earth manufactured solar cells are attached to the sheets.
- the sheets are attached to the pipes to create the modular solar panels.
- the truss structures are created by attaching the pipes with the pipe holders. Because the air lock to space # 15 is small by comparison to the size of the modular solar panel # 18 ( FIG. 5 ), the panels will have to be built in modular pieces. Also, to fit the 100 meter length of the panel out the air lock to space # 15 , the panels will have to be rolled.
- the many pipe segments for 2 pipes # 39 each 100 meters long, with 4 segments having physical and electrical connectors attached # 41 are manufactured and stored in the intertank # 33 ( FIG. 11 ) . Then the airlock to space # 15 is opened. The manipulator robot # 5 - 7 grasps a pipe segment # 39 with physical and electrical connectors # 41 attached and pulls it into space. Then a regular pipe # 39 is attached to the bottom of the first pipe # 39 and the assembly pulled up into space. This process is repeated until the last segment of pipe # 39 , with physical and electrical connectors # 41 is attached to create the 100 meter length. The pipe is stored in one of the 2 solar panel assembly tracks # 16 ( FIG. 5 ). Another pipe is created in the same way and stored in the other solar panel assembly track # 16 .
- a space tug # 24 docks at the remanufacturing plant ( FIG. 3 ), gets grabbed by a manipulator robot # 5 - 7 and is moved to allow it to attach with the solar panel # 18 .
- the clamps on the solar panel assembly track # 16 release, and the space tug # 24 takes the solar panel # 18 away from the remanufacturing plant ( FIG. 3 ). It carries it into nearby orbit, where the rotational spin is removed, and other solar panels # 18 , truss structures ( FIG. 7 ), and modular microwave transmitter arrays # 22 join the group for transport to geosynchronous (GEO) orbit.
- GEO geosynchronous
- truss structures ( FIG. 7 ) will be created for support and electrical management in the solar collection array (# 21 , FIG. 1 ).
- the pipes # 39 will be linked into the truss structures in the machine shop (# 12 , FIG. 4 ), wired up and joined together in 15 meter lengths, and stored in the intertank # 33 . They will be linked together into the correct lengths by pulling them out of the airlock to space # 15 by the manipulator robot (# 5 - 7 , FIG. 3 ) and attaching them together.
- the solar panels # 18 when finished they will be picked up by the space tug # 24 . They will be linked together with the solar panels # 18 and a space tug # 24 for transport into geosynchronous orbit.
- Microwave transmitter elements manufactured on earth, will also be cargo that is delivered to the manufacturing facility. Modular pieces of transmitter arrays (# 22 , FIG. 1 ) will be created by connecting the transmitter elements to truss structures ( FIG. 7 ) and wiring them together. These will manufactured into 15 foot lengths and stored in the intertank # 33 . Then they get connected together into 100 m lengths through the air lock to space (# 15 , FIG. 4 ) using the manipulator robot arms (# 5 - 7 , FIG. 3 ).
- the solar power modules ( FIG. 5 ), the modular transmitter arrays (# 22 , FIG. 1 ), and the truss structures ( FIG. 7 ) will be individually picked up by a space tug ( FIG. 6 ).
- the solar power modules ( FIG. 5 ) will be linked together in nearby space into a 10 grid shape bounded on both ends by a truss structure, with an additional solar power module ( FIG. 5 ) connected to a truss structure ( FIG. 7 ).
- the modular transmitter arrays (# 22 , FIG. 1 ) also link to the truss structure ( FIG. 7 ).
- a space tug ( FIG. 6 ), equipped with electric powered engines (like ion drives) will dock and move the group to geosynchronous orbit (GEO).
- GEO geosynchronous orbit
- the additional solar power module will furnish power to the Space Tug ( FIG. 6 ) for delivery and return.
- the Space Tug ( FIG. 6 ) will disconnect from the 10 grid structure, and connect that structure to the Solar Power Array (# 21 , FIG. 1 ).
- the Space Tug ( FIG. 6 )
- the Space Tug ( FIG. 6 )
- the single remaining solar power module ( FIG. 5 ) returns to the manufacturing facility ( FIG. 3 ) in LEO, and the process repeats until the solar power collection array (# 21 , FIG. 1 ) is collecting the required energy and transmitting it, by the Microwave Transmitter (# 22 , FIG. 1 ) to earth.
Abstract
A geosynchronous Solar Power Satellite System is created by an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels and transmitter arrays. This facility takes empty fuel tanks and expended rocket boosters from launch vehicles that are sent into low earth orbit, and re-manufactures them into structural components. These components are mated to solar cells that are launched from earth. The modular solar panels are transported to geosynchronous orbit by vehicles with ion engines, where the panels are mated to other solar panels to collect power. Structural components are also mated to transmitter elements launched from earth. These are likewise transported to geosynchronous orbit. They are mated to the solar power collecting panels and they beam the collected power back to earth.
Description
- This application is related to U.S. Provisional Patent Application No. 60/680,861, entitled “SOLAR POWER PLAN”, filed May 13, 2005 in the name of Paul Roseman and incorporated by reference into the subject non-provisional application.
- The present invention relates generally to the creation of a geosynchronous Solar Power Satellite System, and more particularly to the creation of an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels, modular transmitter arrays and truss structures.
- In particular, a method of creating a geosynchronous solar power satellite system from a low earth orbit structure with artificial gravity and closed ecology that links re-manufactured expended rocket boosters with solar cells created on earth into modular solar panels. It also links re-manufactured expended rocket boosters with microwave transmitter elements created on earth into modular transmitter arrays. Both the solar panels and transmitter arrays are transported to geosynchronous orbit by electric engines (like ion engines).
-
- 1. Cover Art—Space Manufacturing 9 Proceedings of the Eleventh SSI-Princeton Conference May 1993;
- 2. “Wireless Power Transmission—A Strategy for Decarbonizing Global Energy Use”, Peter E. Glaser, Arthur D. Little, Inc, Space Manufacturing 9 Proceedings of the Eleventh SSI-Princeton Conference May 1993, pp. 335-341;
- 3. “The Equatorial Plane—The International Gateway to Space”, Dr. William C. Brown, Microwave Power Transmission Systems, Space Manufacturing 8 Proceedings of the Tenth SSI-Princeton Conference May 1991, pp. 25-31;
- 4. “Aluminum Salvage Station for External Tanks (ASSET)”, Curtis H. Spenny, James N. Haislip, Robert E. Linscott, William Raynes, Michael Skinner, and David VanMatre, Air Force Institute of Technology, Space Manufacturing 8 Proceedings of the Tenth SSI-Princeton Conference May 1991, pp. 213-224;
- 5. “Further Developments in Very Large Truss Construction in Space”, Anthony P. Coppa, General Electric, Space Manufacturing 7 Proceedings of the Ninth-Princeton/AIAA/SSI Conference May 1989, pp. 162-172;
- 6. “The Space Shuttle Operators Manual”, Kerry Mark Joels, Gregory P. Kennedy, Ballantine Books, New York, 1982;
- 7. “Ranger Telerobotic Flight Experiment Program Update”, Joseph D. Graves, University of Maryland, Space Manufacturing 10 Proceedings of the Twelfth SSI-Princeton Conference May 1995, pp.199-203;
- 8. “Space Solar Power—A Fresh Look at the Feasibility of Generating Solar Power in Space for Use on Earth” Science Applications International Corporation—Harvey Feingold, Michael Stancati, Alan Friedlander, Mark Jacobs, Futron Corporation—Doug Comstock, Carissa Christensen, Greggt Maryniak, Scott Rix, National Aeronautics and Space Administration—John C. Mankins, April 1997, Report Number SIAC-97/1005;
- 9. “Newton—A Variable Gravity Research Facility/Final Report”, The International Space University, 1989; and
- 10. “Space Solar Power Program/Final Report”, The International Space University, 1992.
- In the 1970's Dr. Peter Glaser presented a 5 Gigawatt Solar Power Satellite System. The outer space part consisted of a solar power collector array #21 (
FIG. 1 ) and microwave transmitter #22 (FIG. 1 ) in geosynchronous orbit. The power collected there was beamed to earth where a rectenna #23 (FIG. 1 ) converted the energy into electricity to add to the electrical grid. In his plan the solar collector and microwave transmitter were constructed in geosynchronous orbit by astronauts from modular pieces manufactured on earth. This method proved to be too expensive to be feasible. Subsequently, the microwave power beaming and conversion processes were demonstrated, by Dr. William Brown and others. Since then, many plans have been offered to collect solar power in space. Because of the high cost of launching materials to low earth orbit, and even higher costs to geosynchronous orbit, none of them were economically competitive. - In accordance with the present invention, the low earth orbit manufacturing facility is created. Empty external tanks from Space Shuttle launches are collected in low earth orbit. They are then joined together, filled with habitat, manufacturing, environment recycling modules and engines. They are then rotated to create an artificial “mars normal” gravity environment.
- Then the facility is used to manufacture the modular components of the Solar Power Satellite System. Additional empty external tanks and expended rocket boosters are collected. They are re-manufactured and mated to solar cells manufactured on earth and launched to low earth orbit. Modular solar panels are created. Truss structures are created. Modular transmitter arrays are created by mating transmitter arrays manufactured on earth and launched to low earth orbit, to truss structures. These modular solar panels and modular transmitter arrays are moved to geosynchronous orbit by unmanned vehicles using electric powered engines (like ion engines). Then the solar power panels and transmitter arrays are linked together in geosynchronous orbit to beam power back to earth.
- The foregoing objects and advantage of the present invention may be more readily understood by one skilled in the art with reference being had to the following detailed description of a preferred embodiment thereof, taken in conjunction with the accompanying drawings wherein like elements are designated by identical reference numerals throughout the several views, and in which:
-
FIG. 1 . discloses a prior art solar power satellite system; -
FIG. 2 shows an External Tank (ET) from a Space Shuttle launch. It has been outfitted with 2 solar power, electric engine (like ion drive) devices for station keeping; -
FIG. 3 shows the low earth orbit (LEO) artificial gravity, closed ecology, multi-use structure for manufacturing the solar power panels, the truss structures, and the transmitter arrays; -
FIG. 4 shows a cutaway diagram of an “outer ET” in the previous diagram where, upon rotation, there will be simulated a “mars-normal” artificial gravity environment; -
FIG. 5 shows the low earth orbit (LEO) artificial gravity, closed ecology, multi-use structure with a modular solar power panel constructed and ready to be taken to geosynchronous orbit (GEO); -
FIG. 6 shows the RANGER NPV space vehicle of the prior art from the Space Systems Laboratory with its hands grasping an object; -
FIG. 7 shows the design for a truss structure of the prior art; -
FIG. 8 shows a sub-panel of solar cells being rolled up for construction of the modular solar power panel; -
FIG. 9 shows a collection of modular solar power panels with truss structures, connected to a Ranger for transport to geosynchronous orbit (GEO); -
FIG. 10 shows a Solar Power Satellite, with collection array, and transmitter; -
FIG. 11 shows a cutaway of the Space Shuttle External Tank(ET) of the prior art; -
FIG. 12 shows a Space Shuttle of the prior art; and -
FIG. 13 is a picture label index. - In this preferred embodiment for the current space situation, for the creation of the manufacturing facility, an empty external tank (ET) #1 (
FIG. 2 ) from the Space Shuttle is not discarded upon the Shuttle's launch to the International Space Station (ISS). Instead, the empty external tank (ET) is taken into orbit with the Space Shuttle. About 30 miles short of the International Space Station (ISS), the Shuttle disconnects and undocks from the external tank (ET). - The external tank (ET) is fitted by the Shuttle Manipulator Arm #37 (a standard part of the Space Shuttle) with a station keeping device, which consists of a girdle of solar power cells #18 (
FIG. 2 ) that connects to an ion engine #2 (FIG. 2 ). The Shuttle crew opens the cargo bay doors #38 (FIG. 12 ), and take out a wraparound solar panel with anion engine # 18,2 (FIG. 2 ), using the Shuttle Manipulator Arm #37 (FIG. 12 ). With the Shuttle Manipulator Arm #37 (FIG. 12 ), the Shuttle astronauts attach the wraparound solar panel withion engine # - Then they do this again, putting 2 wraparound solar panels with
ion engines # ion engines # - Two additional ET's are collected on separate missions in a similar fashion, and stored in the same location. Then the next Shuttle mission is dedicated to setting up the manufacturing facility. This will require an additional commercial launch (like the Ariane5), with additional supplies rendezvousing with the group of collected ETs about 30 miles short of the International Space Station (ISS).
- On this mission, the Space Shuttle, still attached to its external tank (ET) rendezvous with the 3 stored ETs and the commercial launch payload at the site short of the ISS. The Shuttle uncouples from its attached ET. The ET is positioned perpendicularly to another ET. The base end of one ET #36 (
FIG. 11 ) is attached to the middle of another ET, creating a “T” like structure. This task is repeated with the other pair of ETs so that 2 “T” structures have been created. - Then the base ends #36 of the ET the forms the top of the “T” are removed. The habitat #10 (
FIG. 4 ),manufacturing # 12,13 (FIG. 4 ) and ecology #11 (FIG. 4 ) modules are loaded into the empty hydrogen tank #34 (FIG. 11 ) of those ETs and then the base ends #36 are reattached. - Then the nose ends #35 (
FIG. 11 ) of the ET that forms the base of the “T” are attached to the docking port #3 (FIG. 3 ) module. The structural cables #4 (FIG. 3 ) are attached. Then the manipulator robots #5-7 (FIG. 3 ) are attached to thestructural cables # 4. The solar power assembly tracks #16 (FIG. 3 ) are attached and then the solar panel assembly robots #17 (FIG. 3 ) are attached to the solar power assembly tracks #16. The ion engines #2 (FIG. 3 ) are repositioned and then they are fired up to start the rotation process to generate artificial gravity. At the distance of 100 m (the distance between the 2 outer ETs), 2 revolutions per minute will simulate a “mars normal” (0.4 of standard earth. gravity) on the outer ETs. And, for the inner ETs, any lesser variable gravity (like “moon normal” can be simulated wherever a floor is built. - The manufacturing facility makes if possible to cheaply and easily remanufacture the empty fuel tanks and booster rockets into solar panels because of its artificial gravity and closed ecology. Many closed ecologies have already been tested here on earth, but only in our gravity environment. Our manufacturing expertise is only in our gravity environment. To make it possible to more cheaply manufacture the solar power collector arrays and transmitter arrays, we first need to create an artificial gravity environment. Such environments in space can be produced most easily by rotation.
- An artificial gravity environment similar to that of Mars could be generated by a structure rotating twice a minute that has a diameter of 300 feet (approx. 100 meters). This is the artificial gravity environment that's best for the manufacturing structure. The martian 0.4 g environment will not have a significant impact on the technologies developed on earth, either the closed-ecology or manufacturing technologies required to build the Solar Power Satellite project.
- Operating costs for the facility will be low, because there is a low need for re-supply. This is directly because of the closed ecology technologies used. We can use Earth normal manufacturing equipment and methodologies, adapted to a closed environment, so they won't be expensive to buy and easy to run. It will be expensive to deliver and remove personnel, so that crew/worker durations will be long. In this embodiment, the remanufacturing facility should be built near the ISS to take best advantage of nearby infrastructure and transportation opportunities. Emergency return vehicles need to be available as lifeboats for the crew.
- The working/living environment will be inside the hydrogen tank #34 (
FIG. 11 ), in the ET, and so doubly shielded from space. Thehydrogen tank # 34 is 100 feet long by 27 feet in diameter. Turned into 2 floors, it would be about 5000 square feet per tank. Inside, various parts would be setup for habitat #10 (FIG. 4 ), foundry #13 (FIG. 4 ), machine shop #12 (FIG. 4 ) and closed-ecology equipment and facilities #11 (FIG. 4 ). - After setting up the modules built on earth—the habitat, ecology and manufacturing modules #10-14, the air lock to space #15 (
FIG. 4 ) needs to be created, cut out of the intertank #33 (FIG. 11 ), #9 (FIG. 4 ). - Solar power modules, 100 meters square, are an output product of the manufacturing facility. The solar cells are manufactured on earth. They will be launched into LEO, aimed at the manufacturing facility. In this preferred embodiment, they will be captured and loaded into the facility. A space tug (
FIG. 6 ) will capture the cargo and transfer it to the manipulator robots #5-7 (FIG. 3 ). The rocket that delivers the solar cells will be cut up and taken into the facility. Machines have been designed to cut ET's into cylindrical chunks. These chunks will be grasped by the manipulator robots #5-7 (FIG. 3 ). These manipulator robots #5-7 (FIG. 3 ) will be teleoperable and be attached to and move up and down the structural cables #4 (FIG. 3 ) with changing gravity at changing distances from the rotation center. These manipulator robots #5-7 (FIG. 3 ) will be needed to unload and store launched solar cells, cargo and the raw material stream. They will deliver them to the air lock to space #15 (FIG. 3 . Everything then gets loaded into the remanufacturing facility through the air lock to plant #14 (FIG. 3 ). - The materials in the stream are already quite refined, being composed of empty fuel tanks, expended rocket boosters and captured “space junk”. Most of the stream is made of aluminum, which is light and easily re-melted and reformed at low (700 deg F.) temperatures. The material stream will be melted down in the foundry #13 (
FIG. 4 ), and turned into building material. The building pieces consist of metal sheets, pipes and pipe holders. The earth manufactured solar cells are attached to the sheets. The sheets are attached to the pipes to create the modular solar panels. The truss structures are created by attaching the pipes with the pipe holders. Because the air lock tospace # 15 is small by comparison to the size of the modular solar panel #18 (FIG. 5 ), the panels will have to be built in modular pieces. Also, to fit the 100 meter length of the panel out the air lock tospace # 15, the panels will have to be rolled. - To manufacture the solar panel #18 (
FIG. 5 ) 15 foot wide rolls of thin aluminum #28 (FIG. 8 ) are created from the materials stream. The solar cells are attached to them, and wired up #27 (FIG. 8 ) to the solar panel bus connection #19 (FIG. 8 ). Then, one end of the roll is mated to a pipe segment #25 (FIG. 8 ). The pipe is rolled as more solar cells are attached and wired up and the other end attached to anotherpipe # 25 after the 100 meter length is completed. Successful testing of the completed product finishes the process. Many of these are produced. Additionally, pipes are produced in 15 foot segments. All pipes connect physically and electrically to the pipe segments above and below them, and some come with physical and electrical connectors #41 (FIG. 7 ) to connect to truss structures and other pipes. They are tested and then put to use. - The many pipe segments for 2
pipes # 39, each 100 meters long, with 4 segments having physical and electrical connectors attached #41 are manufactured and stored in the intertank #33 (FIG. 11 ) . Then the airlock tospace # 15 is opened. The manipulator robot #5-7 grasps apipe segment # 39 with physical andelectrical connectors # 41 attached and pulls it into space. Then aregular pipe # 39 is attached to the bottom of thefirst pipe # 39 and the assembly pulled up into space. This process is repeated until the last segment ofpipe # 39, with physical andelectrical connectors # 41 is attached to create the 100 meter length. The pipe is stored in one of the 2 solar panel assembly tracks #16 (FIG. 5 ). Another pipe is created in the same way and stored in the other solar panelassembly track # 16. - The rolls of solar cells attached to pipes (
FIG. 8 ) are then stored in theintertank # 33. Then the airlock tospace # 15 is opened. The manipulator robot #5-7 grasps a segment, is pulls it up to outer space, then the next segment (FIG. 8 ) is attached. Both pipes #26 get attached to the previous segment. After the twin pipes #26 with the rolled solar cells extend the full 100 meter length, the top and bottom of thepipes # 26 are attached to the solar panel assembly robots #17 (FIG. 5 ). One side of pipes and rolled solar cells are pulled out to the correct length on one side, and attached top and bottom to the pipe physical andelectrical connectors # 41 stored in the solar panel assembly track #16 (FIG. 5 ). Then the other pipe is pulled out to the correct size, and attached to the other physical andelectrical connectors # 41 attached top and bottom at the end of the solar powerassembly track # 16. In this way the modular solarpower panels # 18 are manufactured. - A
space tug # 24 docks at the remanufacturing plant (FIG. 3 ), gets grabbed by a manipulator robot #5-7 and is moved to allow it to attach with thesolar panel # 18. The clamps on the solar panelassembly track # 16 release, and thespace tug # 24 takes thesolar panel # 18 away from the remanufacturing plant (FIG. 3 ). It carries it into nearby orbit, where the rotational spin is removed, and othersolar panels # 18, truss structures (FIG. 7 ), and modular microwavetransmitter arrays # 22 join the group for transport to geosynchronous (GEO) orbit. - In a similar manner, truss structures (
FIG. 7 ) will be created for support and electrical management in the solar collection array (#21,FIG. 1 ). Thepipes # 39 will be linked into the truss structures in the machine shop (#12,FIG. 4 ), wired up and joined together in 15 meter lengths, and stored in theintertank # 33. They will be linked together into the correct lengths by pulling them out of the airlock tospace # 15 by the manipulator robot (#5-7,FIG. 3 ) and attaching them together. As with thesolar panels # 18, when finished they will be picked up by thespace tug # 24. They will be linked together with thesolar panels # 18 and aspace tug # 24 for transport into geosynchronous orbit. - Microwave transmitter elements, manufactured on earth, will also be cargo that is delivered to the manufacturing facility. Modular pieces of transmitter arrays (#22,
FIG. 1 ) will be created by connecting the transmitter elements to truss structures (FIG. 7 ) and wiring them together. These will manufactured into 15 foot lengths and stored in theintertank # 33. Then they get connected together into 100 m lengths through the air lock to space (#15,FIG. 4 ) using the manipulator robot arms (#5-7,FIG. 3 ). - Then the solar power modules (
FIG. 5 ), the modular transmitter arrays (#22,FIG. 1 ), and the truss structures (FIG. 7 ) will be individually picked up by a space tug (FIG. 6 ). The solar power modules (FIG. 5 ) will be linked together in nearby space into a 10 grid shape bounded on both ends by a truss structure, with an additional solar power module (FIG. 5 ) connected to a truss structure (FIG. 7 ). The modular transmitter arrays (#22,FIG. 1 ) also link to the truss structure (FIG. 7 ). A space tug (FIG. 6 ), equipped with electric powered engines (like ion drives) will dock and move the group to geosynchronous orbit (GEO). The additional solar power module will furnish power to the Space Tug (FIG. 6 ) for delivery and return. At geosynchronous orbit the Space Tug (FIG. 6 ) will disconnect from the 10 grid structure, and connect that structure to the Solar Power Array (#21,FIG. 1 ). If there is a modulartransmitter array # 22 with thespace tug # 24 group (FIG. 9 ) then it is attached to thetransmitter array # 22. Then the Space Tug (FIG. 6 ), with the single remaining solar power module (FIG. 5 ) returns to the manufacturing facility (FIG. 3 ) in LEO, and the process repeats until the solar power collection array (#21,FIG. 1 ) is collecting the required energy and transmitting it, by the Microwave Transmitter (#22,FIG. 1 ) to earth. - Although the present invention has been described in terms of various embodiments, it is not intended that the invention be limited to these embodiments. Modification within the spirit of the inventions will be apparent to those skilled in the art. The scope of the present invention is defined by the claims that follow.
-
- 1) External Tank (ET)
- 2) Ion Engine
- 3) Docking Port
- 4) Structural Cable
- 5) Manipulator Robot—Moveable Carriage
- 6) Manipulator Robot—Rotating Arm
- 7) Manipulator Robot—Grasping Claw
- 8) External Tank—Oxygen Tank
- 9) External Tank—Intertank
- 10) Habitat
- 11) Closed Ecology Maintenance
- 12) Machine Shop
- 13) Foundry
- 14) Air Lock to Plant
- 15) Air Lock to Space
- 16) Solar Panel Assembly Track
- 17) Solar Panel Assembly Robot
- 18) Solar Panel
- 19) Solar Panel Bus Connection
- 20) Solar Panel Frame
- 21) Solar Collection Array
- 22) Microwave Transmitter
- 23) Rectenna
- 24) Ranger
- 25) Pipe
- 26) Solar Power Cell
- 27) Solar Cell Wiring
- 28) Solar Cell Backing—Aluminum Roll
- 29) Rotating Cap
- 30) SPS Panels w/Ranger
- 31) Earth
- 32) ET—Liquid Oxygen Tank
- 33) ET—Intertank
- 34) ET—Liquid Hydrogen Tank
- 35) ET—Nose Cap
- 36) ET—Propellant Feed Lines
- 37) Space Shuttle—Manipulator Arm
- 38) Space Shuttle—Cargo Bay
- 39) Truss Structure—Pipe
- 40) Truss Structure—Pipe Holder
- 41) Truss Structures—Physical and Electrical Connector
Claims (4)
1. A habitat for low earth orbit, said habitat comprising:
a) a closed ecology habitat;
b) a manufacturing facility;
c) means for rotating said closed ecology habitat and said manufacturing facility to establish a variable gravity therein; and
d) said manufacturing facility for remanufacturing objects left in space.
2. A method for creating a microwave transmitter in space, said method comprising the steps of:
a) manufacturing at least one element on earth;
b) boosting the one element into low earth orbit;
c) finding and capturing objects left in space;
d) remanufacturing the captured objects into transmitter array devices; and
e) assembling in space the transmitter array devices and the one element.
3. A method of constructing a space station from expended empty booster rockets left in space, said method comprising the steps of:
a) boosting a plurality of station parts from earth into low earth orbit;
b) capturing empty rockets disposed into low earth orbit;
c) assembling first and second empty rockets to each end respectively of a third and fourth empty rocket to form the space station of an “H” configuration;
d) installing said first and second empty rockets modules for a foundry, a machine shop and a habitat for humans; and
e) rotating said space station to create gravity within each of said first, second, third and fourth empty rockets.
4. A method for creating a solar power array in a geosynchronous orbit, said method comprising the steps of:
a) constructing in low earth orbit a manufacturing facility;
b) boosting solar cells manufactured on earth to low earth orbit;
c) assembling at the manufacturing facility a modular solar panel comprised of the boosted solar cells which are connected to the panel; and
d) boosting the modular solar panel into geosynchronous orbit.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/409,697 US7971831B2 (en) | 2005-05-13 | 2006-04-24 | Method for manufacturing a solar module in orbit |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US68086105P | 2005-05-13 | 2005-05-13 | |
US11/409,697 US7971831B2 (en) | 2005-05-13 | 2006-04-24 | Method for manufacturing a solar module in orbit |
Publications (2)
Publication Number | Publication Date |
---|---|
US20090173831A1 true US20090173831A1 (en) | 2009-07-09 |
US7971831B2 US7971831B2 (en) | 2011-07-05 |
Family
ID=40843792
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/409,697 Expired - Fee Related US7971831B2 (en) | 2005-05-13 | 2006-04-24 | Method for manufacturing a solar module in orbit |
Country Status (1)
Country | Link |
---|---|
US (1) | US7971831B2 (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011137050A1 (en) * | 2010-04-27 | 2011-11-03 | Alion, Inc. | Rail systems and methods for installation and operation of photovoltaic arrays |
US20160122041A1 (en) * | 2014-10-08 | 2016-05-05 | Analytical Mechanics Associates, Inc. | Extendable solar array |
US9343592B2 (en) | 2010-08-03 | 2016-05-17 | Alion Energy, Inc. | Electrical interconnects for photovoltaic modules and methods thereof |
US9352941B2 (en) | 2012-03-20 | 2016-05-31 | Alion Energy, Inc. | Gantry crane vehicles and methods for photovoltaic arrays |
US9453660B2 (en) | 2013-09-11 | 2016-09-27 | Alion Energy, Inc. | Vehicles and methods for magnetically managing legs of rail-based photovoltaic modules during installation |
US20160335598A1 (en) * | 2015-02-12 | 2016-11-17 | John Aylmer | Multi-Destination Instrumentation Delivery System for Solar System Exploration to create and sustain commercial, heavy industrial and research opportunities |
US9641123B2 (en) | 2011-03-18 | 2017-05-02 | Alion Energy, Inc. | Systems for mounting photovoltaic modules |
US9657967B2 (en) | 2012-05-16 | 2017-05-23 | Alion Energy, Inc. | Rotatable support system for mounting one or more photovoltaic modules |
US9988776B2 (en) | 2015-09-11 | 2018-06-05 | Alion Energy, Inc. | Wind screens for photovoltaic arrays and methods thereof |
US10122319B2 (en) | 2013-09-05 | 2018-11-06 | Alion Energy, Inc. | Systems, vehicles, and methods for maintaining rail-based arrays of photovoltaic modules |
US10189583B2 (en) * | 2015-05-13 | 2019-01-29 | Analytical Mechanics Associates, Inc. | Deployable sheet material systems and methods |
US20220041302A1 (en) * | 2020-04-22 | 2022-02-10 | Timothy N. Sippel | Gyromesh solar sail spacecraft and sail panel assemblies |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8882048B2 (en) | 2011-05-20 | 2014-11-11 | Eugene M. Levin | In-space processing and delivery system |
US10654596B1 (en) | 2016-09-29 | 2020-05-19 | Northrop Grumman Systems Corporation | On-orbit thermal extractions of raw materials from space debris in support of additive manufacturing of new space elements on-orbit |
US11045678B1 (en) * | 2020-12-04 | 2021-06-29 | Richard Dattner | Systems and methods for modular recreational structures |
Citations (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4057207A (en) * | 1976-04-08 | 1977-11-08 | John Paul Hogan | Space vehicle module |
US4078747A (en) * | 1974-08-13 | 1978-03-14 | Phaser Telepropulsion, Inc. | Orbiting solar power station |
US4579302A (en) * | 1984-03-09 | 1986-04-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Shuttle-launch triangular space station |
US4667907A (en) * | 1984-11-19 | 1987-05-26 | General Dynamics Corporation/Convair Div. | Space based orbit transfer vehicle |
US4685535A (en) * | 1985-07-31 | 1987-08-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Mobile remote manipulator vehicle system |
US4702440A (en) * | 1985-10-14 | 1987-10-27 | Erno Raumfahrttechnik Gmbh | Satellite station |
US4728060A (en) * | 1984-03-09 | 1988-03-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space station architecture, module, berthing hub, shell assembly, berthing mechanism and utility connection channel |
US4730797A (en) * | 1985-08-12 | 1988-03-15 | Minovitch Michael Andrew | Inflatable core orbital construction method and space station |
US4744533A (en) * | 1986-08-25 | 1988-05-17 | Mullen Charles F | Modular space station |
US4765114A (en) * | 1986-11-13 | 1988-08-23 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Expandable pallet for space station interface attachments |
US4776541A (en) * | 1985-09-24 | 1988-10-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fluidic momentum controller |
US4792108A (en) * | 1986-07-24 | 1988-12-20 | Bull Stephen M | Space station |
US4796394A (en) * | 1987-11-13 | 1989-01-10 | Chastain Lemuel J | Geodesic structure |
US4805368A (en) * | 1986-11-13 | 1989-02-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Expandable pallet for space station interface attachments |
US4807834A (en) * | 1984-03-09 | 1989-02-28 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Space station architecture, module, berthing hub, shell assembly, berthing mechanism and utility connection channel |
US4807833A (en) * | 1986-04-11 | 1989-02-28 | Pori James A | Combined space vehicle fuel cell and space station structural building component |
US4817895A (en) * | 1985-06-18 | 1989-04-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Aerobraking orbital transfer vehicle |
US4821914A (en) * | 1988-04-01 | 1989-04-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Low temperature storage container for transporting perishables to space station |
US4858857A (en) * | 1988-12-30 | 1989-08-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking mechanism for spacecraft |
US4860975A (en) * | 1988-12-30 | 1989-08-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Smart tunnel - docking mechanism |
US4878637A (en) * | 1986-08-25 | 1989-11-07 | Mullen Charles F | Modular space station |
US4898348A (en) * | 1988-12-30 | 1990-02-06 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking system for spacecraft |
US4966806A (en) * | 1986-12-16 | 1990-10-30 | Foster Miller, Inc. | Film-based structural components with controlled coefficient of thermal expansion |
US5017820A (en) * | 1990-04-23 | 1991-05-21 | Rockwell International Corporation | Piezoelectric rotary union system |
US5016418A (en) * | 1986-08-22 | 1991-05-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Synchronously deployable double fold beam and planar truss structure |
US5092545A (en) * | 1990-05-09 | 1992-03-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of delivering lunar generated fluid to earth orbit using an external tank |
US5094409A (en) * | 1990-05-09 | 1992-03-10 | The Bionetics Corporation | Method of providing a lunar habitat from an external tank |
US5102150A (en) * | 1991-02-19 | 1992-04-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Pressure vessel flex joint |
US5143327A (en) * | 1990-08-31 | 1992-09-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Integrated launch and emergency vehicle system |
US5184789A (en) * | 1991-02-12 | 1993-02-09 | Buzz Aldrin | Space station facility |
US5225632A (en) * | 1990-09-05 | 1993-07-06 | Fairchild Space And Defense Corporation | Space utility conduit |
US6045094A (en) * | 1996-11-04 | 2000-04-04 | Rivera; Ramon L. | Gyroscopic space ship/station with docking mechanism |
US6206328B1 (en) * | 1998-11-09 | 2001-03-27 | Thomas C. Taylor | Centrifugal gravity habitation torus constructed of salvaged orbital debris |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5244406A (en) | 1992-09-21 | 1993-09-14 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Spline screw payload fastening system |
US5407152A (en) | 1992-12-24 | 1995-04-18 | The United States Of America As Represented By The Administrator Of National Aeronautics & Space Administration | Pre-integrated truss space station and method of assembly |
US5580013A (en) | 1994-12-20 | 1996-12-03 | Velke; William H. | Economical construction and assembly method for a modular permanent orbiting space station |
US5865401A (en) | 1996-08-29 | 1999-02-02 | Space Systems/Loral, Inc. | Tethered space platform assembly for isolation orbiting |
US5833329A (en) | 1996-10-03 | 1998-11-10 | Mcdonnell Douglas Corporation | Lightweight rack |
JP4026840B2 (en) | 1996-11-04 | 2007-12-26 | ラモン エル リベラ | Gyroscopic spacecraft / space station with docking mechanism |
-
2006
- 2006-04-24 US US11/409,697 patent/US7971831B2/en not_active Expired - Fee Related
Patent Citations (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4078747A (en) * | 1974-08-13 | 1978-03-14 | Phaser Telepropulsion, Inc. | Orbiting solar power station |
US4057207A (en) * | 1976-04-08 | 1977-11-08 | John Paul Hogan | Space vehicle module |
US4728060A (en) * | 1984-03-09 | 1988-03-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Space station architecture, module, berthing hub, shell assembly, berthing mechanism and utility connection channel |
US4579302A (en) * | 1984-03-09 | 1986-04-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Shuttle-launch triangular space station |
US4807834A (en) * | 1984-03-09 | 1989-02-28 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Space station architecture, module, berthing hub, shell assembly, berthing mechanism and utility connection channel |
US4667907A (en) * | 1984-11-19 | 1987-05-26 | General Dynamics Corporation/Convair Div. | Space based orbit transfer vehicle |
US4817895A (en) * | 1985-06-18 | 1989-04-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Aerobraking orbital transfer vehicle |
US4685535A (en) * | 1985-07-31 | 1987-08-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Mobile remote manipulator vehicle system |
US4730797A (en) * | 1985-08-12 | 1988-03-15 | Minovitch Michael Andrew | Inflatable core orbital construction method and space station |
US4776541A (en) * | 1985-09-24 | 1988-10-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fluidic momentum controller |
US4702440A (en) * | 1985-10-14 | 1987-10-27 | Erno Raumfahrttechnik Gmbh | Satellite station |
US4807833A (en) * | 1986-04-11 | 1989-02-28 | Pori James A | Combined space vehicle fuel cell and space station structural building component |
US4792108A (en) * | 1986-07-24 | 1988-12-20 | Bull Stephen M | Space station |
US5016418A (en) * | 1986-08-22 | 1991-05-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Synchronously deployable double fold beam and planar truss structure |
US4744533A (en) * | 1986-08-25 | 1988-05-17 | Mullen Charles F | Modular space station |
US4878637A (en) * | 1986-08-25 | 1989-11-07 | Mullen Charles F | Modular space station |
US4765114A (en) * | 1986-11-13 | 1988-08-23 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Expandable pallet for space station interface attachments |
US4805368A (en) * | 1986-11-13 | 1989-02-21 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Expandable pallet for space station interface attachments |
US4966806A (en) * | 1986-12-16 | 1990-10-30 | Foster Miller, Inc. | Film-based structural components with controlled coefficient of thermal expansion |
US4796394A (en) * | 1987-11-13 | 1989-01-10 | Chastain Lemuel J | Geodesic structure |
US4821914A (en) * | 1988-04-01 | 1989-04-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Low temperature storage container for transporting perishables to space station |
US4858857A (en) * | 1988-12-30 | 1989-08-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking mechanism for spacecraft |
US4898348A (en) * | 1988-12-30 | 1990-02-06 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Docking system for spacecraft |
US4860975A (en) * | 1988-12-30 | 1989-08-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Smart tunnel - docking mechanism |
US5017820A (en) * | 1990-04-23 | 1991-05-21 | Rockwell International Corporation | Piezoelectric rotary union system |
US5092545A (en) * | 1990-05-09 | 1992-03-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of delivering lunar generated fluid to earth orbit using an external tank |
US5094409A (en) * | 1990-05-09 | 1992-03-10 | The Bionetics Corporation | Method of providing a lunar habitat from an external tank |
US5143327A (en) * | 1990-08-31 | 1992-09-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Integrated launch and emergency vehicle system |
US5225632A (en) * | 1990-09-05 | 1993-07-06 | Fairchild Space And Defense Corporation | Space utility conduit |
US5184789A (en) * | 1991-02-12 | 1993-02-09 | Buzz Aldrin | Space station facility |
US5102150A (en) * | 1991-02-19 | 1992-04-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Pressure vessel flex joint |
US6045094A (en) * | 1996-11-04 | 2000-04-04 | Rivera; Ramon L. | Gyroscopic space ship/station with docking mechanism |
US6206328B1 (en) * | 1998-11-09 | 2001-03-27 | Thomas C. Taylor | Centrifugal gravity habitation torus constructed of salvaged orbital debris |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9655292B2 (en) | 2010-04-27 | 2017-05-16 | Alion Energy, Inc. | Methods of making photovoltaic arrays and rail systems |
US20110284057A1 (en) * | 2010-04-27 | 2011-11-24 | Alion, Inc. | Rail systems and methods for installation and operation of photovoltaic arrays |
WO2011137050A1 (en) * | 2010-04-27 | 2011-11-03 | Alion, Inc. | Rail systems and methods for installation and operation of photovoltaic arrays |
US9462734B2 (en) * | 2010-04-27 | 2016-10-04 | Alion Energy, Inc. | Rail systems and methods for installation and operation of photovoltaic arrays |
US9343592B2 (en) | 2010-08-03 | 2016-05-17 | Alion Energy, Inc. | Electrical interconnects for photovoltaic modules and methods thereof |
US9641123B2 (en) | 2011-03-18 | 2017-05-02 | Alion Energy, Inc. | Systems for mounting photovoltaic modules |
US9352941B2 (en) | 2012-03-20 | 2016-05-31 | Alion Energy, Inc. | Gantry crane vehicles and methods for photovoltaic arrays |
US9657967B2 (en) | 2012-05-16 | 2017-05-23 | Alion Energy, Inc. | Rotatable support system for mounting one or more photovoltaic modules |
US10122319B2 (en) | 2013-09-05 | 2018-11-06 | Alion Energy, Inc. | Systems, vehicles, and methods for maintaining rail-based arrays of photovoltaic modules |
US9453660B2 (en) | 2013-09-11 | 2016-09-27 | Alion Energy, Inc. | Vehicles and methods for magnetically managing legs of rail-based photovoltaic modules during installation |
US9937846B2 (en) | 2013-09-11 | 2018-04-10 | Alion Energy, Inc. | Vehicles and methods for magnetically managing legs of rail-based photovoltaic modules during installation |
US9856039B2 (en) * | 2014-10-08 | 2018-01-02 | Analytical Mechanics Associates, Inc. | Extendable solar array for a spacecraft system |
US20160122041A1 (en) * | 2014-10-08 | 2016-05-05 | Analytical Mechanics Associates, Inc. | Extendable solar array |
US20160335598A1 (en) * | 2015-02-12 | 2016-11-17 | John Aylmer | Multi-Destination Instrumentation Delivery System for Solar System Exploration to create and sustain commercial, heavy industrial and research opportunities |
US10189583B2 (en) * | 2015-05-13 | 2019-01-29 | Analytical Mechanics Associates, Inc. | Deployable sheet material systems and methods |
US20190263540A1 (en) * | 2015-05-13 | 2019-08-29 | Analytical Mechanics Associates, Inc. | Deployable sheet material systems and methods |
US10815012B2 (en) * | 2015-05-13 | 2020-10-27 | Analytical Mechanics Associates, Inc. | Deployable sheet material systems and methods |
US9988776B2 (en) | 2015-09-11 | 2018-06-05 | Alion Energy, Inc. | Wind screens for photovoltaic arrays and methods thereof |
US20220041302A1 (en) * | 2020-04-22 | 2022-02-10 | Timothy N. Sippel | Gyromesh solar sail spacecraft and sail panel assemblies |
US11958637B2 (en) * | 2020-04-22 | 2024-04-16 | Geoshade Corporal | Gyromesh solar sail spacecraft and sail panel assemblies |
Also Published As
Publication number | Publication date |
---|---|
US7971831B2 (en) | 2011-07-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7971831B2 (en) | Method for manufacturing a solar module in orbit | |
Li et al. | On-orbit service (OOS) of spacecraft: A review of engineering developments | |
US7559508B1 (en) | Propellant depot in space | |
CN111406022A (en) | Spacecraft service device and related components, systems and methods | |
EP0541052A1 (en) | Spacecraft system | |
US20080078886A1 (en) | Launch vehicle cargo carrier | |
EP3305666B1 (en) | A spacecraft, a method and a system | |
US20100038491A1 (en) | System and method for transferring cargo containers in space | |
CN113631481A (en) | Spacecraft service device and related components, systems and methods | |
EP1578665A1 (en) | Service vehicle for performing in-space operations on a target spacecraft, servicing system and method for using a service vehicle | |
CN112207530B (en) | Spacecraft on-orbit assembly method based on polymer robot | |
WO2009148625A2 (en) | Space station, launch vehicle, and method of assembly | |
Cichan et al. | Mars base camp updates and new concepts | |
US20050241691A1 (en) | Space Construction | |
Palii | State of the art in the development of orbital industrial platforms | |
Dubanchet et al. | EROSS Project–Coordinated control architecture of a space robot for capture and servicing operations | |
JP2021504248A (en) | How to launch an artificial satellite into orbit around the earth | |
Austin et al. | The ubiquitous solar electric propulsion stage | |
Akin et al. | Enabling Dexterous Manipulation and Servicing by SmallSats | |
Belyaev et al. | From the First Manned Mission into Space to the Permanently Manned Orbital Station | |
Howard | A Permanent Human Lunar Surface Presence Enabled By a CLV Class JUMP Lander | |
ODell et al. | The Mars Base Camp Re-Usable Crewed Descent and Ascent Vehicle | |
Raj et al. | Catalyst: An Orbit Platform for Accelerating the Advancement of the Cislunar Economy | |
WO2023025942A1 (en) | Method and system for a scalable and reconfigurable space infrastructure | |
CN115157675A (en) | Space assembly system based on-orbit additive manufacturing and foundation launching fusion |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
REMI | Maintenance fee reminder mailed | ||
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20150705 |